Beagle B-206 N1885S

Summary

On 16 May 1998 at about 12:50 local time, a Beagle B-206 registered N1885S was involved in an accident near Vernon, Texas, United States. 3 people were on board and 3 died. The aircraft was destroyed. The NTSB has published a probable cause for this accident; it is quoted in full below.

Date

16 May 1998 at 12:50

Classification

Accident

Location

Vernon, Texas, United States

Coordinates

34.1405, -99.2992

Aircraft

Beagle B-206

Registration

N1885S

Category

Airplane

Engines

2

Operator

Not recorded

Operating rule

Part 91: General Aviation

Purpose of flight

Personal

Phase of flight

Not recorded

Route

Unknown → Austin

Aircraft damage

Destroyed

Weather

VMC

Light

Day

NTSB number

FTW98FA216

3 people died.

The pilot's failure to maintain the airplane's minimum controllable airspeed following a loss of left engine power after takeoff, which resulted in a loss of control. Contributing factors were the fractured exhaust valve guide on the left engine's # 2 cylinder, the fatigue failure of the #2 cylinder's exhaust valve, and subsequent failure of the left engine's turbocharger resulting from foreign object damage.

Quoted verbatim from the NTSB record. This site does not paraphrase or interpret it.

Read the full NTSB narrative

According to witnesses, the twin-engine airplane took off and was climbing when a reduction in engine power was heard. The airplane was observed leveling off, and a left turn back to the airport was initiated. The airplane was observed in level flight for a few seconds and then it rolled to the left and impacted on a highway in a nose low attitude. A post impact fire destroyed the airplane. The logbooks for the airplane and engines were not made available during the investigation. The minimum controllable airspeed (Vmc) was listed at 76 mph in a brochure provided by the previous owner of the airplane. Examination of the left engine revealed that the #2 cylinder's exhaust valve had failed in fatigue. Closer examination of the exhaust valve and its guide revealed that a portion of the valve guide was missing. Carbon deposits on the valve stem provided evidence that the engine had been operated for some period of time in this condition. Examination of the left turbocharger revealed that it was not rotating at the time of the accident; however, its turbine wheel blades displayed foreign object damage, more than likely resulting from portions of the separated exhaust valve head passing through the turbocharger. Examination of the propellers revealed that neither propeller was in the feather position at the time of the impact, and the left propeller was being operated at no or low power at impact. The left propeller control lever was found in the aft (feather) position.

Quoted verbatim from the NTSB record.